Aeroplane



Sept. l, 1931. D. c. ROBERTS 1,821,323

AEROPLANE Filed March 17, 1930 .2 Sheets-Sheet 1 l. mumm||||||..........E

Sept.' l, 1931. 1,821,323

D. c. ROBERTS AEROPLANE 2 Sheets-Sheet 2 yFiled March 17, 1930 Patented Sept. l, 1931 4'lnxrnla'l OFFICE DANIEL C. ROBERTS, OF TRENTON, NEWl JERSEY AEROPLAN E Application ledrMarch 17, 1930. Serial No. 436,572.

This Ainvention appertains to aeron'autics and more particularly to a novel and improved aeroplane andglider construction.

vOne of the primary 'objects of my invention is to provide a novel sustaining wing extending the full length ofthe aeroplane fuselage of a substantially hexagonal shape in plan embodying a transversely extending front leading edge and a transversely extending rear trailing edge with oppositely inclined front and rear leading andl trailing egges extending from said first mentioned e ges.

Another important object of my invention is the provision of vertical wing or lateral surfaces depending from the wings and arranged on opposite sides of the fuselage forming an efficient means for sustaining the aeroplane in iight against side slip and facilitating the banking and turning of the aeroplane.

A further object of my invention' is the provision of a novel vane carried by the vertical side wing or surfaces below the fuselage mounted on a horizontal pivot and capable of movement tor a vertical position below the vertical wing faces and between the fuselage and said vertical wing faces t'o form an eincienty air brake to lessen the speed of the aeroplane in the air and to facilitate the landing thereof in a small landing field", the vane also forming an e'licient means for permitting the gaining of altitude during the take-off of the aeroplane, said vane being adapted to'be disposed at an angle to the horizontal to facilitate the climbing of the aeroplane.

A further object of my invention is the provision of a novel wing, vane and side vertical faces for an aeroplane, which can be used with any preferred type of fuselage, thereby allowing the conventional type of fuselage to be used with the aeroplane.

A further object of my invention` is to increase the safety in the flying of aeroplanes and render the usual aeroplane of a stronger and sturdier design.

A still further object of my invention is to provide an improved aeroplanek of the above character, whichgwill be durable .and

efficient in use, one that will be simple and easy to manufacture, and one which can be placed .upon the market at a reasonable cost.

With these and other objects in view, the invention consists in the novel construction, arrangement and formation of parts, as will be hereinafter more specifically described, claimed, and illustrated in the accompanying drawings, in which drawings Figure l is a side elevation of my improved `30 aeroplane. v

Figure 2 is a t'op plan view of the same.

Figure 3 is a front elevation of my aeroplane.

Figure 4 is a bottom kplan view of the same.

Figure 5 is a transversely sectional view through the improved plane taken on the line 5 5 of Figure llooking in the direction of the arrows.

Referringto the drawings in detail, wherevin similar reference characters designate corresponding parts throughout the several views, the letter A generally indicates my improved aeroplane which comprises a longitudinally extending fuselage 10 which may be of the usual orany-preferred shape and construction forming the'support for the engine, pilot seat and the like. The fronty of the fuselage may carry the usual or any preferred typeof tractor propeller 11. u

Connected with the fuselage lOin any preferred way is my improved wing or sustaining surface 15, which forms an important part ofmy present invention. In the present showing Iv have illustrated a single wing or` in other words a monoplane, but it is to be understood that two` or more wings can be utilized without departing from thespirit or the scope of my invention to provide a` biplane or a triplane. y Likewise, if desired, this wing can ybe of a hollow construction to `form a reservoir or tank for fuel or the like or'as means for receiving a lighter than air gas.

` In accordance with my invention the wing l5 extends the full length ofl or substantially the full length of the fuselage 10 and is of a substantially hexagonal shape in plan embodying a straight transversely extending tending vertically disposed'win'g'surfaces 2O- and 21 which are arranged on opposite sides of the fuselage 10 in spaced parallel relation thereto. These lateralor. vertical wing surfaces and 21 may likewise extend the full length of the fuselage,` if' desired, but' the same preferably taper rearwardly t'o theltail ofthe fuselage. Y

In' order toprovid'e effieientmeans for supporting andy strengthening the side lateral or vertical wing surfaces 2O and 21, I can provide upper and` lower longitudinals or spars 22 and23, theupp'erlongitudinale being connected to'the'wingl 15 to f'orm a brace therefor. Ibikewise a transversely extending main spar 24 can be provided which extends across Vtlie upperlongit'udinal spars 22 andhas its 'terininalslc'onnected tothe wing' tips.` The front and rear longitudinal spars 22 and 23 can be connected together by transverse brace bars 25 and vertical uprights or standards 26. Likewise diagonal braces-'27 may lead from the longitudinal spars t'o the'fuselagey 10. I also'can"provide` brace bars27" for the'wing tips and theseY brace bars can lead to' the 'wingtips through the longitudinal' spars23. "'Ilie'provision'` of the side lateral or vert'ical wing's120'and 21:forms another salient part ofi my invention, as by the use of'these side laterallsurfaees I am enabled t`o facilitate the e'veirtravel of the aeroplane' through the air and to permit the efficient turning of the aeroplane inthe air.'

The aeroplane may be providedV with any preferred type'ofl landing gear# elither for ground or water and in the'presen't` instance I have shown the'lower'longitudinalv spars 23 adjacent to the forward ends thereof' provided withj ground wheels 28. Likewise a longitudinally extending tail? skid'29'is provided, and it is to ber noted that this tailskid extends a material distance forwardly from thereart'ip" of the fuselage and'isy covered to provide a depending iin 30. Tlierear end'of tli'e fuselage can likewise sup'port'the usual tailpieces 31 whichmay Yembody' t'he vertical and horizontal rudders and? stabilizers.

Fori'ni'ngk another and salient featurelof any' invention is the front transversely extending vane35and this vane is so constructed andv arranged as't'o constitute both a liftin'g'. surface, when in one ofits'positions and as a wind"k break' when in another one of its positions'. l

This vane 35 extends between and entirely Leanszs across the lateral side or vertical wings 20 and 21 and a horizontal pivot 36 is provided therefor which pivot is carried by the lowe'r longitudinal spars 23. The pivot is located substantially equally distant the front and rear edges of the vane, as clearly shown in Figure 2 ofi the drawings. Any desired means canlbe provided for operating the vane 35, .such as a hand lever secured to the pivot 35 extending into the fuselage through a suitableA slot' formed thereon. The hand lever canY carry a pawl for locking engagement with a segmental rack secured to the fuselage.

Inuse of the vane, when itis desired to take off from a field or to gain altitude the vane' isset at an' angle to the horizontal inclining upwardly toward the front of thel aeroplane. This provides a lifting surface and permits thev quickgaining of altitude by the aeroplane.V

Then it' is desired to lessen the forward speed of the aeroplane' in' landing and the like the rear edge ofthe vane 35 is swung upwardly so that the vane will occupy a sub'- stantially vertical position with the rear edges thereof in contactV with the lower'surface ofv the wingV 15. The rear edge of the vane is cut away as at 37 so that the vane will t' about the fuselage when the same is swung to its vertical position and this' out' out portion 37' provides sidetail' extensions 38 which lie in between'the fuselage' and the' side lat.- eralor vertical wings`-20 and 21 to prevent the passage of Aair through' the' aeroplane `between the fuselage and said wings20'and 21.. By this arrangement the vane will act as'an effi cient air break'and'stopV the'forward' travel of the aeroplane.' 'Ilhus it can beA seen that' I have provided an aeroplane which can land in a'n exceedingly restricted area.

The aeroplane an'dv its various parts can be constructed from any desired type of-material' such as-allwoodl, all metal, or a combinavtion ofwoed, metal' and fabric. Infact any desired material and arrangement can b'e used.

In reducing my invention to practice, various minor changes in thedetails of construction may be' necessary,'but' without sacrificing anv ofthe advantages ofv my invention, as denedv in the appended claims;

What I claim as new is:

1. In an aeroplane, a longitudinally extending fuselage, a sustaining wing connect-` ed with the fuselage and'extending substantiallythe full length thereof.longitudinally extending. vertically disposed wingssecured to and depending from` the sustaining wing onopposite sides-of the fuselage in -spacedrelation thereto, a vane arranged' between the yertical wings, a horizontaly pivot for 'said vaneV arrangedintermediate the ends thereof, whereby said-vane can=beswung to a Vertical position or at'` an. angle'tb'thei'fvertical andato the horizontal, and means for operating said Vane.

2. In an aeroplane, a longitudinally eX- tending fuselage, asustaining wing connected with the fuselage and extending substantially the full length thereof, longitudinally extending vertically disposed wings secured to and depending from the sustaining wing on opposite sides of the fuselage inspaced relation thereto, a vane arranged between the vertical wings, a horizontal pivotfor said vane arranged intermediate the ends thereof, whereby said vane can be swung to a vertical position or at an angle to the Vertical and to the horizontal, means for operating said Vane, the rear end of said vane being notched for receiving the fuselage when the vane is swung to a vertical position, the notch deliningside piece-s for lying between the fuselage and the vertical wings and for engaging the sustaining wing.

In testimony whereof I affix my signature.

DANIEL C. ROBERTS. 

